RU2323855C2 - Aircraft missile system - Google Patents

Abstract

FIELD: engines and pipes.

SUBSTANCE: aircraft missile system contains airplanes, airframe, in the fuselage of which it is disposed the booster rocket of airborne device of mating the booster rocket with the airplane, making the function of the towing vehicle, and systems providing their functioning, and surface-mounted transport-booster platform, equipped with engines for its boosting. On the rocket fuselage it is additionally installed the cowling with additional wing on it, and brad with tail cowling. On the tail cowling it is installed the stabilization device and rudder unit. The cowlings are made with possibility of being removed from the rocket.

EFFECT: it is achieved the exceeding of the distance of flight and it is arisen the cargo mass of space objects bringing to the orbit.

3 cl, 1 dwg

Description

The invention relates to the field of aerospace rocket and space technology. It can be used in aeronautical missile complexes (ARC) for space purposes, mainly with heavy ballistic missiles (weighing 100 tons or more), equipped with, for example, liquid rocket engines (LRE) and launched in the air with the aim of launching spacecraft (SC), for example, a satellite in orbit.

A known analogue of the ARC with an air launch launcher towed by several aircraft is presented in the description of RF patent No. 2130879 (1999). The specified analogue as the closest in technical essence adopted as a prototype.

The disadvantages of the prototype are including:

- the need to use for towing a launch vehicle (LV) aircraft with increased power of their propulsion systems;

- low efficiency of using the technical capabilities of aircraft, for example, in the range of LV delivery to its launch point;

- the complexity of pairing the launch vehicle with towing aircraft, as well as the launch method of the launch vehicle;

- big risks in the implementation of the ARC creation program.

The tasks to which the invention is directed are

- increasing the efficiency of using the technical capabilities of towing aircraft and the ARC as a whole;

- improving the safety and reliability of launch;

- reduction of technical, financial risks during the creation of the ARC and during its operation.

This is achieved by including:

- the use of aircraft as rocket towers to the launch point;

- use of the ground transportation and booster platform (TRP), on which the loaded LV is mounted;

- use of a simple-by-design device for interfacing a LV with towing aircraft;

- application of a simplified launch method of the launch vehicle.

The invention is illustrated in Fig.1-3, which shows a General view of the placement of the launch vehicle (LV) on the ground TRP, the connection of the LV with aircraft, performing the functions of towing LV.

RN 1 with additional fairings 2 mounted on its body with wing 3 mounted on it, front (nose) 4 and tail 5 fairings is located on the ground TRP 6. Wing 3 is mounted on the PH 1 housing with its center section 7 and fairing 2, the cable the halyard 8 is interfaced with the center wing 7 of the wing 3 and the airplane 9. Aircraft 9 and 10 are successively (one after another) interfaced with a halyard cable 11. The front fairing 4 and the tail fairing 5 are mounted on the front (nose) and tail parts of the hull of the PH 1, respectively . Stabilizing surfaces are mounted on the tail fairing 5, forming a controlled stabilizer 12 and a vertical tail unit 13. Moreover, the fairings 2, 4, 5 are made with the possibility of separating them from the body 2 of the PH 1, for example, using detonating elongated charges or pyro locks mounted on these fairings, for the destruction of their power ties with the body of the PH 1 (not shown). The wing 3 is equipped with ailerons 14, the stabilizer 12 - elevators 15, and the tail 13 - rudders 16. In the wing 3 of the fairing 2, the center section 7 of the wing 3, in the front and tail fairings 4, 5, if necessary, cavities for placement of system elements can be made control PH 1, wing 3, stabilizer 12, for example, the vertical tail unit 13 and their power supply, for example, electric batteries and other systems that ensure the functioning of the ARC (not shown).

The ropes-halyards 8, 11, the plane 9, the center wing 7 of the wing 3, the fairing 2 form a device for interfacing the PH 1 with the towing aircraft 10.

This system, including the pH 1, aircraft 9, 10 and other aforementioned elements, operates as follows.

Before launching the spacecraft, the ground-based TRP 6 is fed to the technical position of the aviation missile complex, where it is loaded with the loaded launch vehicle 1, for example, with uncharged fuel components with the aforementioned elements mounted on it.

After loading the equipped RN 1 to the TRP 6, the PH 1 is refueled and its systems, as well as the TRP 6 systems are checked for functioning.

After completing all the work on preparing the aviation missile system for launching the spacecraft, the equipped TRP 6 is towed to the runway (runway) 17 to the starting point of the TRP 6 when take-off aircraft 9, 10 to launch RN 1, where the aircraft 9 is connected to the center section 7 of the wing 3 mounted on the fairing 2 with the help of a cable-rope 8, and pairing the planes 9, 10 with each other sequentially (one after another) using the cable-rope 11. As a result, the planes 9, 10 and TRP 6 are brought to the starting position on runway 17.

The functioning of the complex is carried out in the following sequence.

On command from the ARC control system, engines are launched simultaneously on planes 9, 10 and TRP 6 to take off for the missile launch area (engines 18 are installed on it to accelerate TRP 6). The thrusts of the engines of aircraft 9, 10 and TRP 6 provide equal acceleration when moving along the runway 17.

Upon reaching the specified thrust levels of the engines of towing aircraft 9, 10 and TRP 6, a take-off command is sent from the ARC control system (the start of their movement along runway 17).

At the same time, the thrust levels of the engines of aircraft 9, 10 and engines 18 of the TRP 6 are provided, excluding the sagging of the hitch cables 8, 11 to unacceptable levels.

When aircraft 9, 10 and TRP 6 move along runway 17, lift forces act on planes 9, 10 and curb launch vehicle 1, which ensure separation of planes 9, 10 from runway 17 and curb launch vehicle 1 from TRP 6 when the desired speed is reached (~ 280 -300 km / h).

When aircraft 9, 10 are separated from runway 17 at the same time from TRP 6, the equipped RN 1 is separated by command, for example, from the RN 1 control system and the start of the flight of 9, 10 aircraft to the launch site of RN 1.

Upon the arrival of aircraft 9, 10 to the launch area, aircraft 9, 10 and equipped PH 1 occupy specified design positions in space in terms of altitude, direction and flight speed, angular parameters (roll, pitch, course), ensuring launch of PH 1.

On command from the ARC control system to launch the launch vehicle 1, commands are issued to start the engine of the first stage of the launch vehicle 1, the separation of the cowls 2, 4, 5, wing 3 with center wing 7 from the housing of the launch vehicle 1, for example, by using pyrozamas and detonating elongated charges, placed on these detachable elements (not shown in the drawing) to destroy their power ties with the body of the PH 1.

After separation from the body of the launch vehicle 1 of all the above-mentioned parts mounted on it and starting the engine of the first stage, it is flown according to a given program and the spacecraft is put into a given orbit.

Thus, the above technical appearance of the ARC with new distinctive features in comparison with the prototype allows, including:

- at lower financial costs and time required for the creation of the ARC, to increase its effectiveness;

- increase safety, reliability and simplify the operation of the ARC;

- simplify the technology of manufacturing and testing of ARC systems during their creation;

- reduce technical and other risks during the creation of the ARC and its operation.

The technical solution proposed in the invention opens up a promising direction for the development of the ARC.

Claims (3)

1. Aviation missile system, including airplanes, an air launch vehicle, a device for interfacing a launch vehicle with airplanes that perform the functions of a launch vehicle tow, systems that ensure their operation, characterized in that it contains a ground transport and booster platform equipped with engines, on which the launch vehicle is mounted, a fairing additionally mounted on the launch vehicle body, on which a wing with a center wing, equipped with ailerons, is mounted, nose and hv cowls a skeleton on which stabilizing surfaces are mounted, forming a controlled stabilizer and, for example, a vertical tail unit, while all fairings are made with the possibility of separation from the body of the launch vehicle, the first and second planes are sequentially paired with the first halyard cable, while the second plane with the help of the second hitch rope, it is interfaced with the wing center wing mounted on a fairing mounted on the carrier rocket body, while both the hitch rope and the second aircraft together with the wing, the center wing ohms of the wing and its fairing form a device for interfacing a carrier rocket with a towing aircraft. 2. The aviation missile system according to claim 1, characterized in that in the cavities mounted on the carrier rocket of the nose and tail fairings, the fairing of the wing and its center section there are elements of the control systems of the launch vehicle, wing, stabilizing surfaces and their power supply, for example, electric accumulators . 3. The aviation missile system according to claim 1, characterized in that the ground transport and booster platform is equipped with a control system.

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